Abstract

An investigation was made to determine the effect of Reynolds number on the flow about a cone of 70 degrees apex angle with free stream Mach numbers close to the Mach number for shock attachment.

Conditions existing on the forward half of a one-half inch diameter cone were investigated at two Mach numbers, one giving a slightly detached shock and one giving a slightly attached shock, at Reynolds numbers from 150,000 to 1,300,000 based on model diameter.

Close to the apex the static pressure on the surface of the cone divided by the stagnation pressure before the shock was found to be dependent upon the Reynolds number at the lowest Reynolds number when the shock was detached but not when the shock was attached. In both cases at a distance half way back on the cone there was a continuous increase in this ratio with increasing Reynolds number. All of these Reynolds number effects were small in magnitude.

The investigation was conducted in the GALCIT 2.5” Supersonic Wind Tunnel.